EH 2.5/10 (eh2510-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.5/10 (eh2510-il) Reynolds number: 100,000 Max Cl/Cd: 47 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2510-il-100000.txt Download as CSV file: xf-eh2510-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.5/10
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4829 0.10563 0.10104 0.0018 1.0000 0.0870
-9.000 -0.4935 0.10253 0.09803 -0.0032 1.0000 0.0895
-8.750 -0.5096 0.09915 0.09476 -0.0096 1.0000 0.0902
-8.500 -0.4872 0.09387 0.08948 -0.0052 1.0000 0.0937
-8.250 -0.4801 0.09043 0.08606 -0.0053 1.0000 0.0970
-8.000 -0.4842 0.08668 0.08239 -0.0080 1.0000 0.1003
-7.750 -0.4120 0.07433 0.07038 -0.0113 1.0000 0.1093
-7.500 -0.4157 0.07028 0.06638 -0.0129 1.0000 0.1123
-7.250 -0.4298 0.06623 0.06237 -0.0149 1.0000 0.1153
-7.000 -0.4617 0.06266 0.05859 -0.0197 1.0000 0.1188
-6.500 -0.4882 0.06373 0.05934 -0.0176 1.0000 0.1218
-6.250 -0.4759 0.06056 0.05616 -0.0169 1.0000 0.1274
-6.000 -0.4713 0.05699 0.05241 -0.0175 1.0000 0.1360
-5.750 -0.4579 0.05411 0.04952 -0.0167 1.0000 0.1437
-5.500 -0.4479 0.05095 0.04631 -0.0159 1.0000 0.1538
-5.250 -0.4378 0.04829 0.04361 -0.0148 1.0000 0.1680
-5.000 -0.4294 0.04585 0.04115 -0.0133 1.0000 0.1825
-4.500 -0.4035 0.03581 0.02943 -0.0095 0.9940 0.0892
-4.250 -0.3563 0.03010 0.02290 -0.0128 0.9784 0.0748
-4.000 -0.3070 0.02644 0.01870 -0.0167 0.9631 0.0731
-3.750 -0.2573 0.02412 0.01571 -0.0202 0.9459 0.0774
-3.500 -0.2107 0.02164 0.01311 -0.0234 0.9276 0.0822
-3.250 -0.1702 0.02011 0.01127 -0.0248 0.9052 0.0899
-3.000 -0.1378 0.01877 0.00994 -0.0250 0.8829 0.1069
-2.750 -0.1125 0.01774 0.00890 -0.0238 0.8592 0.1333
-2.500 -0.0905 0.01687 0.00824 -0.0222 0.8385 0.1734
-2.250 -0.0701 0.01603 0.00764 -0.0204 0.8180 0.2243
-2.000 0.0928 0.01451 0.00815 -0.0386 0.8010 0.9883
-1.750 0.1377 0.01434 0.00760 -0.0421 0.7798 1.0000
-1.500 0.1577 0.01438 0.00739 -0.0407 0.7606 1.0000
-1.250 0.1783 0.01443 0.00723 -0.0395 0.7434 1.0000
-1.000 0.1991 0.01450 0.00708 -0.0383 0.7275 1.0000
-0.750 0.2199 0.01458 0.00696 -0.0371 0.7126 1.0000
-0.500 0.2410 0.01466 0.00688 -0.0360 0.6984 1.0000
-0.250 0.2624 0.01476 0.00683 -0.0349 0.6846 1.0000
0.000 0.2841 0.01487 0.00681 -0.0339 0.6715 1.0000
0.250 0.3059 0.01500 0.00682 -0.0329 0.6589 1.0000
0.500 0.3278 0.01514 0.00684 -0.0320 0.6471 1.0000
0.750 0.3497 0.01528 0.00686 -0.0309 0.6360 1.0000
1.000 0.3716 0.01544 0.00690 -0.0298 0.6250 1.0000
1.250 0.3937 0.01563 0.00705 -0.0289 0.6133 1.0000
1.500 0.4158 0.01584 0.00720 -0.0280 0.6024 1.0000
1.750 0.4379 0.01604 0.00732 -0.0270 0.5927 1.0000
2.000 0.4601 0.01625 0.00746 -0.0260 0.5827 1.0000
2.250 0.4821 0.01652 0.00774 -0.0251 0.5720 1.0000
2.500 0.5043 0.01678 0.00795 -0.0241 0.5627 1.0000
2.750 0.5267 0.01702 0.00813 -0.0230 0.5536 1.0000
3.000 0.5486 0.01734 0.00848 -0.0221 0.5433 1.0000
3.250 0.5709 0.01764 0.00877 -0.0211 0.5345 1.0000
3.500 0.5934 0.01792 0.00903 -0.0202 0.5256 1.0000
3.750 0.6153 0.01831 0.00948 -0.0193 0.5158 1.0000
4.000 0.6382 0.01860 0.00972 -0.0183 0.5081 1.0000
4.250 0.6602 0.01898 0.01019 -0.0174 0.4983 1.0000
4.500 0.6823 0.01940 0.01066 -0.0164 0.4892 1.0000
4.750 0.7057 0.01968 0.01090 -0.0155 0.4815 1.0000
5.000 0.7272 0.02018 0.01153 -0.0146 0.4716 1.0000
5.250 0.7501 0.02057 0.01195 -0.0137 0.4634 1.0000
5.500 0.7728 0.02095 0.01242 -0.0128 0.4546 1.0000
5.750 0.7945 0.02149 0.01308 -0.0119 0.4453 1.0000
6.000 0.8191 0.02176 0.01330 -0.0110 0.4381 1.0000
6.250 0.8397 0.02234 0.01408 -0.0101 0.4277 1.0000
6.500 0.8618 0.02286 0.01474 -0.0092 0.4188 1.0000
6.750 0.8860 0.02315 0.01505 -0.0083 0.4106 1.0000
7.000 0.9064 0.02382 0.01593 -0.0073 0.4004 1.0000
7.250 0.9291 0.02426 0.01647 -0.0064 0.3913 1.0000
7.500 0.9534 0.02453 0.01679 -0.0056 0.3823 1.0000
7.750 0.9736 0.02515 0.01768 -0.0045 0.3714 1.0000
8.000 0.9954 0.02561 0.01829 -0.0035 0.3610 1.0000
8.250 1.0188 0.02569 0.01846 -0.0025 0.3492 1.0000
8.500 1.0413 0.02478 0.01754 -0.0010 0.3290 1.0000
8.750 1.0603 0.02370 0.01645 0.0009 0.3032 1.0000
9.000 1.0784 0.02332 0.01618 0.0026 0.2807 1.0000
9.250 1.0936 0.02327 0.01634 0.0044 0.2528 1.0000
9.500 1.0972 0.02406 0.01699 0.0071 0.1735 1.0000
9.750 1.0783 0.02771 0.01978 0.0110 0.0892 1.0000
10.000 1.0667 0.03053 0.02241 0.0143 0.0716 1.0000
10.250 1.0564 0.03280 0.02471 0.0176 0.0641 1.0000
10.500 1.0445 0.03553 0.02743 0.0195 0.0594 1.0000
10.750 1.0385 0.03829 0.03026 0.0205 0.0552 1.0000
11.000 1.0345 0.04110 0.03313 0.0208 0.0506 1.0000
11.250 1.0321 0.04378 0.03575 0.0217 0.0477 1.0000
11.500 1.0410 0.04565 0.03765 0.0237 0.0449 1.0000
11.750 1.0534 0.04743 0.03953 0.0253 0.0424 1.0000
12.000 1.0645 0.04946 0.04162 0.0265 0.0400 1.0000
12.250 1.0876 0.05211 0.04417 0.0287 0.0364 1.0000
12.500 1.0921 0.05490 0.04723 0.0292 0.0357 1.0000
12.750 1.0938 0.05821 0.05082 0.0295 0.0352 1.0000
13.000 1.0938 0.06173 0.05458 0.0294 0.0351 1.0000
13.250 1.0881 0.06578 0.05888 0.0289 0.0351 1.0000
13.500 1.0793 0.07011 0.06345 0.0278 0.0351 1.0000
13.750 1.0671 0.07498 0.06855 0.0262 0.0352 1.0000
14.000 1.0532 0.08016 0.07394 0.0240 0.0354 1.0000
14.250 1.0381 0.08571 0.07969 0.0214 0.0356 1.0000
14.500 1.0207 0.09185 0.08601 0.0183 0.0358 1.0000
14.750 1.0031 0.09835 0.09267 0.0148 0.0361 1.0000
15.000 0.9840 0.10549 0.09996 0.0109 0.0363 1.0000
15.250 0.9682 0.11229 0.10693 0.0067 0.0367 1.0000
15.500 0.9427 0.12126 0.11609 0.0000 0.0373 1.0000
15.750 0.8489 0.15260 0.14754 -0.0206 0.0450 1.0000
16.000 0.8431 0.16022 0.15513 -0.0238 0.0461 1.0000
16.250 0.8421 0.16640 0.16129 -0.0263 0.0467 1.0000
16.500 0.6558 0.17882 0.17422 -0.0270 0.1071 1.0000
16.750 0.6519 0.18258 0.17799 -0.0294 0.1070 1.0000
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Polar data table (+)
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